(v)  
Position yaw damper to OFF.

(w)  
Open No. 4 isolation valve. Record difference between steps (t) and (w) as leakage for feel computer null and for feel cylinders. Check that flow does not exceed 1500 cc/min.

(x)  
Switch system B flight controls to OFF.

(y)  
Check that flaps are positioned to approximately 25 units.

(z)  
Check that alternate flap switch is positioned to ARM.

503 
Aug 01/94  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  29-00 Page 613 

(aa) Check that flap handle is positioned to 40 units and record reading as new basic reference flow.
503 29-00 Jun 20/88
Page 614
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

(ab) Open ground interconnect valve. Record difference between steps (aa) and (ab) as reference flow which includes system A relief valve and ground spoilers. Check that flow does not exceed 500 cc/min.
(ac) Position flap handle to zero units. Record difference between steps (ab) and (ac) as
T.E. flap motor case drain leakage. Check that flow does not exceed 3000 cc/min.
(ad) Position flap handle to 25 units, position alternate flap switch to OFF and let flaps stabilize. Record difference between steps (ac) and (ad) as leakage for T.E. flap control valve at null position. Check that flow does not exceed 8000 cc/min.
(ae) Position flap handle to zero units and let flaps stabilize. Record difference between steps (ad) and (ae) as leakage for leading edge flaps and slats. Check that flow does not exceed 500 cc/min.
(af)  Position flap lever to 25 units and let flaps stabilize.
(ag) Position alternate flap switch to ARM.
(ah) Position flap lever to 40 units and record as new basic reference flow.
(ai)  Switch system A spoilers to ON. Record difference between steps (ah) and (ai) as leakage with flight spoilers No. 3 and 6 retracted. Check that flow does not exceed 500 cc/min.
(aj)  Position control wheel approximately 40 degrees clockwise. Record difference between steps (ai) and (aj) as null leakage for flight spoiler No. 6. Check that flow does not exceed 2000 cc/min.
(ak) Position control wheel approximately 40 degrees counterclockwise. Record difference between steps (ak) and (ai) as null leakage for flight spoiler No. 3. Check that flow does not exceed 2000 cc/min.
(al)  With control wheel centered, position speed brake handle half way between ARMED and FLIGHT detent. Record difference between steps (al) and (ah) as null leakage for flight spoilers No. 3 and 6.  Check that flow does not exceed 4000 cc/min.
502 
Oct 20/88  29-00 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Page 615 

(am) Return speed brake handle to DOWN and position system A spoilers switch to OFF. Record reading as new basic reference flow.
(an) Position system A flight controls switch to ON. Record difference between steps (am) and (an) as null leakage for aileron power control unit. Check that flow does not exceed 3000 cc/min.
(ao) Position control wheel fully CW against wheel stops and record reading. Record difference between steps (am) and (ao) as leakage for aileron cylinder and bleed. Check that flow does not exceed 1500 cc/min. If flow exceeds 1500 cc/min, center control wheel and repeat test.
(ap) With control wheel centered, ensure autopilot switch is DISENGAGED and record reading as new basic reference flow.
(aq) Deleted
(ar) Deleted
(as) Open No. 3 isolation valve. Record difference between steps (ap) and (as) as leakage for elevator power control unit null and for tab lock cylinder. Check that flow does not exceed 3000 cc/min.
(at)  Position control column fully aft against column stops and record reading. Record difference between steps (ap) and (at) as leakage for elevator cylinder and bleed. Check that flow does not exceed 1500 cc/min. If flow exceeds 1500 cc/min, return column to neutral and repeat test.
(au) With control column in neutral, record reading as new basic reference flow.
(av) Deleted (aw) Deleted
502 
29-00 Page 616  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jan 20/83 

(ax) Open No. 2 isolation valve. Record difference between steps (au) and (ax) as null leakage for rudder power control unit. Check that flow does not exceed 3000 cc/min.
(ay) Push rudder pedal for full right rudder against pedal stop. Record difference between steps (au) and (ay) as leakage for rudder cylinder and bleed. Check that leakage does not exceed 1200 cc/min. If flow exceeds 1200 cc/min, center the pedals and repeat test.
(az) With rudder pedals in neutral and yaw damper OFF, record reading as new basic reference flow.
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 液壓 HYDRAULIC POWER(14)